Rotary jet engine



April 16, `1963 w. T. KlTcHx-:Ns 3,085,399

ROTARY JET ENGINE Filed May 5, 1961 4 Sheets-Sheet 1 l\ M gs Wcwomu April 16, 1963 w. T. KlTcHENs 3,085,399

ROTARY JET ENGINE Filed May 5, 1961 4 Sheets-Sheetl 2 INVENTOR. WML/,4M 7.- e/Tcws/vs,

April 16, 1963 w. T. KITCHENS ROTARY JET ENGINE 4 Sheets-Sheet 3 Filed May 5, 1961 INVENTOR.

WML/4M 7. ,e/ Tof/Ems,

Trae/VERS.

April 16, 1963 w. T. KlTcHENs 3,085,399

ROTARY JET ENGINE Filed May 5, 1961 4 Sheets-Sheet 4 Mw/Wm" A rraeA/Eys 3,085,399 Patented Apr. 16, 1963 3,085,399 ROTARY JET ENGINE William T. Kitchens, 1216 Pioneer Road, West Palm Beach, Fla. Filed May 5, 1961, Ser. No. 108,074 8 Claims. (Cl. dil-39.35)

This invention relates to power plants, and more particularly to an engine of the rotary jet type.

A main object of the invention is to provide a novel and improved rotary jet engine which is relatively simple in construction, which provides high output, and which provides smooth and eicient operation.

A further object of the invention is to provide an improved rotary jet engine which involves relatively inexpensive components, which is rugged in construction, and which is extremely economical in utilization of fuel.

A still further object of the invention is to provide an improved rotary jet engine which is relatively compact in size, which has high capacity, and which is provided with means for efficiently mixing the air and fuel admitted thereto and for developing a high output pressure in the resultant mixture for delivery to the firing chambers of the engine.

A still further object of the invention is to provide an improved rotary jet engine which is relatively light in weight in proportion to the power rating thereof, which is easy to install, and which is provided with self-contained means for thoroughly and efficiently mixing the fuel and air admitted thereto to provide the proper combustible mixture for operating the engine.

Further objects and advantages of the invention will become apparent from the following description and claims, and from the accompanying drawings, wherein:

FIGURE 1 is a horizontal cross sectional view taken through a rotary jet engine constructed in accordance with the present invention.

FIGURE 2 is a cross sectional view taken substantially on the line 2 2 of FIGURE 1.

FIGURE 3 is an enlarged vertical cross sectional View taken substantially on the line 3 3 of FIGURE l.

FIGURE 4 is a horizontal cross sectional view taken on the line 4 4 of FIGURE 3.

FIGURE 5 is a horizontal cross sectional View taken on the line 5 5 of FIGURE 3.

FIGURE 6 is an enlarged cross sectional view taken substantially on the line 6 6 of FIGURE 2.

FIGURE 7 is a plan view of a fragmentary peripheral portion of the rotor of the engine of FIGURE l, said view being taken substantially on the line 7 7 of FIGURE 2.

FIGURE 8 is a cross sectional View similar to FIGURE 6 but showing a modified form of firing chamber which may be employed in the engine of the present invention.

Referring to the drawings, and more particularly to FIGURES l to 7, 11 generally designates an improved rotary jet engine constructed in accordance with the present invention. The engine 11 comprises a generally circular main housing 12 which is secured on a base portion 13 in which is journaled the output shaft 14 of the engine. The wall 15 of housing 12 opposite base portion "13 is formed with a plurality of air inlet openings 16 for admitting air into the housing for subsequent mixture with liquid fuel in a manner presently to be described. The housing is provided at its periphery with a plurality of exhaust conduits 17 for discharging the gaseous products of combustion of the engine into the atmosphere.

Designated at 13 is a drum-shaped inner housing which is rotatably mounted concentrically with the main housing 12 and which is rotatably supported at its bottom wall 19 on a bearing bushing 20 provided on the hub 21 of an inner gear 22 splined to the shaft 14. At its opposite end the housing drum 18 is rotatably supported on a bearing bushing 24 rotatably engaged on the enlarged top portion 25 of shaft y14 and extending between said enlarged shaft portion and an integral bearing sleeve 26 formed in the wall 15 of the main housing. The enlarged upper portion 25 of shaft 14 is formed with an outwardly extending ange 27 formed with radial passages 28 communicating with a central bore 29 formed in shaft portion 25, and communicating with a plurality of outlet conduits 30 secured in the outer ends of the passages 28 and connecting said passages to the space immediately adjacent the periphery of the top portion of a generally cylindrical rotor member 31 rigidly secured on shaft 14, for example, by being splined thereto in the manner illustrated in FIGURE 3.

The rotor member "31 is formed at its periphery with a plurality of inclined outwardly projecting radial vanes 32 which are arranged in evently spaced peripheral rows. Rigidly secured to the inside surface of the drum member y18 is a generally cylindrical shell member 33 formed with horizontally extending, inwardly projecting evenly spaced bale plates 34 which extend into the spaces defined between the rows of peripheral vanes 32, as shown in FIGURE 3, and which cooperate with the vanes 32 in a manner presently to be described to thoroughly atomize and mix liquid fuel with air to provide a homogeneous mixture thereof at high pressure at the lower portion of the member 18.

As shown in FIGURE 3, the top Wall 35 of the drum member I8 is formed with air admission apertures 36 located over the annular space between the main body portion of rotor member 31 and shell member 33, so that air may be admitted directly into said annular space.

A liquid fuel supply manifold 37 is secured in the top end portion of the stationary bushing 24, fuel being admitted into the manifold 37 from a fuel supply line 38, as shown in FIGURE 2. An annular conduit member 69 is threadedly engaged in the top end portion of shaft element 25 and extends rotatably through the bottom wall 40 of the liquid fuel supply manifold 37, the conduit member 39 being formed with a conical seat 41. A conical valve element 42 is mounted on a depending valve rod 43 which extends slidably and axially through the top wall 44 of manifold 37 and which is biased towards the valve Seat 41 by a coiled spring 45 surrounding the stem member 43 and bearing between the conical valve 4Z and the wall 44, suitable washers 45 being interposed between the top end of the spring and wall 44, as shown in FIGURE 3. The upstanding rod 43 is formed at its top end with a ball element 46 which is rotatably received in a spherical socket 47 carried by a control rod 48 pivoted at 49 to an opstanding bracket 50 mounted on the top wall 15 of main housing 12, whereby to regulate the admission of liquid fuel from the manifold 37 into the conduit 39, and thence to the annular space defined between the main body of the rotor element 31 and the shell member l33.

Designated at 51 is a ring gear which is secured on the bottom wall 19 of the inner housing -18 concentrically with the shaft 14 and which is gearingly coupled to the gear 22 by a pair of diametrically opposite idler gears 52, 52 which meshingly engage between the ring gear 51 and the central gear 22, the idler gears 52 being journaled between top and bottom annular plate members 53 and 54 mounted for free rotation around the axis of shaft 14. Thus, the upper plate member 53 rotatably engages with a bearing ring 56 surrounding the portion of shaft 14 between rotor member 31 and gear 22, and the lower plate member 54 rotatably engages between the reduced sleeve portion 57 of the bearing bushing 20 and the inner circular edge of the annular bottom Wall 119.

Thus, rotation of the inner housing y18, produced by combustion of the fuel mixture, as will be presently described, drives the housing A18 in a clockwise direction, as viewed in FIGURE 1, transmitting torque through the planetary gears 52, S2 and the gear 22 to the shaft `14, causing the shaft 14to be driven in a counterclockwise direction.

It will be noted that the vanes 34 move in a clockwise direction with the drum member 18, whereas the vanes 30 move in a counterclockwise direction with the rotor member 31 so that the elements 34) and 34 move past each other at a relatively high speed, traveling in opposite directions. The liquid fuel admitted into the annular space containing the elements 30 and 34 is thus engaged by and completely atomized by the rapidly moving vanes 32 and baffle elements 34, and the inclined vane elements 32 build up a substantial pressure in the mixture of air and fuel thus produced, which is relatively high at the lower end of the member 1S. The difference in pressure thus causes air to be drawn into the top end of the housing 18 through the air admission aperture 36 by suction and to be aspirated into the annular space be tween the rotor member 31 and the shell 33 to be homo-v gencously mixed therein with the atomized fuel.

Secured to the lower end portion of the inner housing 1S are a plurality of evenly spaced arcuate rigid conduits 60 which are secured at their outer ends to respective combustion chambers 61 (FIGURE 6) the conduits 60 communicating with annular fuel admission spaces `62 dened within the combustion chamber 61 by the annular venturi conduits 63 secured in the -forward ends of the chambers, as shown in FIGURE V6.

The chambers 61 comprise air scoop intake portions 64 at their forward ends communicating with the inwardly convergent forward end portions of the venturi conduits 63. The venturi conduit members 63 are formed with apertures 66 through which the liquid fuel and air mixture from the space 62 is admitted into the venturi member 63 from the associated supply conduit 60, a check valve 67 being provided between the end of each supply conduit 69 and its associated fuel mixture admission space 62, as shown in FIGURE 6. r1`he check valve 67 is of the spring-operated type and is arranged so that it will not open unless a predetermined minimum pressure exists in the associated supply tube 60, whereby the supply of air and fuel will be cut olf when the pressure thereof drops below a minimum limiting value. Furthermore, since the chamber 62 is subjected to the pressure developed in the communicating portions of the venturi member 63, the pressure in the space 62 will aid the spring, and the check valve will close unless the fuel supply pressure is sufficient to overcome the combined effects of the spring and the pressure in the space 62.

Each tiring chamber y61 is formed with a relatively enlarged intermediate main combustion chamber portion 69 in which is mounted a suitable ignition device, such as a spark plug 70 for igniting the fuel and air mixture introduced into the combustion chamber. It will be noted that the fuel and air mixture furnished from the associated supply space 62 is further mixed with air admitted into the combustion chamber through the venturi member 63. The resultant products of combustion are exhausted from the combustion chamber through the outlet opening 71 provided at the end of the combustion chamber opposite the air intake scoop portion -64 and subsequently are discharged through the exhaust conduits 17.

As shown in FIGURE 7, an annular baffle plate 73 is secured over the combustion chambers y61, the bale plate 73 being formed with a plurality of evenly spaced arcuate openings 74 dened beneath upwardly struck arcuate louvers 75 which act as air scoop elements. The louvers 75 are inclined upwardly and forwardly in the direction of rotation of the combustion chambers 61 so that they serve as air scoop elements to drive air downwardly bed neath the batiie member 73 and in the path of movement. of the intake ends 64 of the venturi members 63 mounted in the forward ends of the combustion chambers. It will be noted that the forward portions of the venturi mem-- bers 63 are formed with slots '77 to admit air into thev fuel supply spaces 62 so that this air may be mixed with the fuel mixture in the supply spaces and may be furnished to the rear portions of the venturi members 63l through the discharge openings 66, creating a further' mixture of air and atomized liquid fuel and aiding in the Complete diffusion of the atomized liquid fuel with the air admitted into the firing portions I69 of the combustion chambers.

The ignition device 70 may be timed in any suitable manner and may be operated in conjunction with any conventional distributor arranged to provide proper timing of the spark provided by the member 7)` with the power strokes of the engine. Thus, as shown in FIG- URE 2, the associated distributor system may be controlled by a photo cell -arranged to receive a light beam from a light source 81, the light source y81 being mounted on the base element 13 and the photo cell 80 being mounted on the top wall 15 of the main housing, the beam of light being interrupted intermittently by the arcuate conduit element 6i) as housing 1S rotates. Thus, the timing of ignition will depend upon the positions of the combustion chambers 61 around the axis of the engine, and the devices 70 will fire each time the firing chambers 61 are in predetermined positions relative to the main housing 12.

In operation, when the combustible fuel mixture is ignited in the firing spaces 69, the rapid combustion of the fuel mixture produces a reaction tending to propel the firing chambers 61 forwardly, namely, to the right, as viewed in FIGURE 6, producing a clockwise torque on the housing 18, rotating said housing and developing a counterclockwise torque on the output shaft 14, as viewed in FIGURE 1. The air and fuel is continuously supplied through the annular space between shell 33 and rotor member 3l, being atomized and mixed in said space, as above described, and. being delivered to the com-- bustion chambers 61 under substantial pressure. The atomized fuel and air is further mixed with air and diffused as above described in the forward end portions of the combustion chambers and is admitted into the firing portions 69 to be ignited by the ignition devices 7G. As shown in FIGURE 2, the annular cover plate 73 is secured to a ring member 82 forming part of an annular framework comprising a cooperating ring member 83 and connecting rod 84. The combustion chambers 61 are rigidly secured, as by welding, or the like, to the intermediate portions of the transverse connecting rods 84.

In the modified form of the invention illustrated in FIGURE 8, the ring chambers are somewhat dierent in construction from those previously described, each firing chamber comprising a generally cylindrical main body secured to the connecting rods 84, said main body being provided at its forward portion with an annular venturi-forming member 91 provided with an axialV stem member 92 secured to a cruciform supporting bracket 93 fastened in the forward end portion of the cylindrical member 90 and likewise in the forward por-- tion of the venturi member 91. The stern member 92 is integrally formed at its rear end with a concave rearwardly facing cup-like head element 95 defining an annular venturi space 96 with respect to the rear portion of the main venturi member 91. Said main venturi member 91 is formed at its peripheral portion with an annular fuel receiving cavity 97 communicating with the midportion of the venturi member 91 through radial passages 98.

The cylindrical body members 9) are secured on bracket members 99, which are in turn rigidly secured on the ends of the conduits 60, the members 99 being formed Ywith cavities 100 and being provided with inwardly open` ing flap valves 101, serving the same function as the check valves `67 previously described, the flap valves 101 opening in response to a predetermined pressure of the fuel mixture in the conduits 60 and allowing said fuel mixture to be `admitted into the spaces 100. The spaces i) communicate with the annular fuel supply spaces 97 of the venturi members 91, as is clearly shown in FIGURE 8. As in the previously described form of the invention, the fuel mixture is admitted into the intermediate portions of the venturi members 91, being mixed with air entering the forward end portions of the members 9i) through the forward ends of the venturi members 91, being further mixed with the air and being discharged through the annular venturi-shaped spaces 96 into the interior of the combustion chambers, to be there ignited by the ignition devices 70 in the same manner as previously described.

Annular exhaust venturi members 106 are provided in the rear end portions of the cylindrical bodies 90, to provide for the discharge of the products of combustion from the combustion chambers 90 in a manner to develop a substantial amount of thrust. As in the previously described form of the invention, the reaction developed by the discharge of the combustion gases produces the driving torque to rotate the housing 18 in a clockwise direction, as viewed in FIGURE l, the torque being ultimately applied to the output shaft 14 to drive same in a counterclockwise direction.

As shown in FIGURE 3, a conductive slip ring 111 is mounted on the top wall 3S of housing 1S, being suitably insulated therefrom by means of an annular insulating member 112 secured to the top wall 35 and formed with a seat in which the slip ring 111 is secured. A suitable brush 113 is provided, said brush being mounted in the wall 15 of the main housing 12 and engaging the slip ring 111. The brush 113 is suitably insulated from wall 15, for example, by the use of a suitable insulating bushing. The brush 113 is electrically connected to the output of the ignition system associated with the engine. Respective ignition wires 114 connect the slip ring 111 to the ignition devices '70, the ignition wires 114 being suitably insulated and being mounted on the respective outwardly extending conduits 60.

The speed of the engine may be controlled by varying the supply of fuel admitted to the engine between Ithe valve element 4Z and the annular valve seat member 39, namely, by varying the angle of rotation of the control lever 4S.

While a specific embodiment of an improved rotary jet engine has been disclosed in the foregoing description, it will be understood that various modifications within the spirit of the invention may occur to those skilled in the art. Therefore, it is intended that no limitations be placed on the invention except `as defined by the scope of the appended claims.

What is claimed is:

1. A rotary jet engine comprising a main housing having air inlet and outlet passages, an output shaft journaled in said main housing, a rotor secured on said output shaft and having outwardly projecting compressor vanes, an inner housing rotatably mounted on said shaft and hav* ing air inlet means opening into said main housing adjacent said air inlet passages, a space being provided between said inner housing and said rotor, outwardly projecting rigid conduits secured to said inner housing and communicating with the space between said inner housing and said rotor, respective jet combustion chambers mounted on the ends of said conduits, said chambers having venturi air intake elements communicating with said conduits and having air scoop portions at their forward ends communicating with said venturi elements, fuel ignition means in said jet combustion chambers, said jet combustion chambers having exhaust conduits at their rear ends adjacent said outlet passages, said chambers being positioned substantially normal to radii of said output shaft, whereby to effect rotation of the chambers by jet reaction, means gearingly coupling said inner housing to said output shaft, and means to admit liquid fuel into the space between the inner housing and said rotor.

2. A rotary jet engine comprising a main housing having air inlet and outlet passages, an output shaft journaled in said main housing, a rot-or secured on said output shaft and having outwardly projecting compressor vanes, an inner housing rotatably mounted on said shaft and having air inlet means opening into said main housing adjacent said air inlet passages, a space lbeing provided between said inner housing and said rotor, inwardly projecting baille elements on said inner housing extending adjacent said vanes, outwardly projecting rigid conduits secured to said inner housing and communica-ting with the space between said inner housing and said rotor, respective jet combustion chambers mounted on the ends of said conduits, said chambers having venturi air intake elements, fuel ignition means in said jet combustion chambers, said jet combustion chambers having exhaust conduits at their rear ends adjacent said outlet passages, said chambers being positioned substantially normal t-o radii of said output shaft, whereby to effect rotation of the chambers by jet reaction, means .gearingly coupling said inner housing to said output shaft and being constructed and arranged to rotate the output shaft in a direction opposite to the direction o-f rota-tion of the inner housing, and means to admit liquid fuel into the space -between the inner housing and said rotor.

3. A rotary jet engine comprising a main housing having air inlet and -outlet passages, an output shaft journaled in said main housing, a rotor secured on said output shaf-t and having outwardly projecting compressor vanes, a generally cylindrical inner housing rotatably mounted on said shaft and having air inlet means opening into said main housing adjacent said air inlet passages, a space being provided between said inner housing and said rotor, inwardly projecting baflle elements on said inner housing extending adjacent said vanes, outwardly projecting rigid conduits secured to said inner housing and communicating with the space between said inner housing and said rotor, respective jet combustion charnbers mounted on the ends of said conduits, said chambers having venturi air intake elements communicating with said conduits and having air scoop por-tions at their for- Ward ends communicating with said venturi elements, fuel ignition means in said jet combustion chambers, said jet combustion chambers having exhaust conduits at their rear ends adjacent said outlet passages, said chambers being positioned substantially normal to radii of sai-d output shaft, whereby to effect rotation of the chambers by jet reaction, a ring gear mounted on said inner housing coaxially therewith, a driven gear mounted on said shaft concentrically with said ring gear, means gearingly coupling said ring gear to said driven gear and being constructed and arranged to rotate the output shaft in a direction opposite to the direction o-f rotation of the inner housing, and means to admit liquid fuel into the space between the inner housing and said rotor.

4. A rotary jet engine comprising a main housing having air inlet and outlet passages, an output shaft journaled in said main housing, a rotor secured on said output shaft and having outwardly projecting compressor vanes, a generally cylindrical inner housing rotatably mounted on said shaft and having air inlet means opening into said main housing adjacent said air inlet passages, a space being provided between said inner housing and said rotor, inwardly projecting baffle elements on said inner housing extending adjacent said vanes, outwardly projecting rigid `conduits secured to .said inner housing and communicating with the space between said inner housing and said rotor, respective jet combustion chambers mounted `on the ends of said conduits, said chambers having venturi air intake elements communicating with said conduits and having air scoop portions at their forward ends communicating with said venturi elements, fuel ignition means in said jet combustion chambers, said jet combustion chambers having exhaust conduits at their rear ends adjacent said -outlet passages, said chambers being positioned substantially normal to radii of said output shaft, whereby to effect rotation of the chambers by jet reaction, a ring gear mounted on said inner housing coaxially therewith, a driven gear mounted on said shaft concentrically with said ring gear, a plurality of planetary gears disposed between and gearingly connecting said ring gear to said driven gear, whereby to lrotate the output shaft in a direction opposite to the direction of rotation of the inner housing, and means to admit liquid `fuel into the space between the inner housing and said rotor.

5. A rotary jet engine comprising a support, an output shaft journaled on said support, a rotor secured on said output shaft and having outwardly projecting radial inclined compressor vanes, a generally cylindrical housing member rotatably mounted on said shaft and having air inlet means at one end portion Ifor admitting air into said one end portion, inwardly projecting baille elements on said housing member extending adjacent said vanes, outwardly projecting rigid -conduits secured to and communicating with the other end portion of the housing member, respective jet combustion chambers mounted on the outer ends of said conduits, said chambers having venturi air intake elements, fuel ignition means in said jet combustion chambers, said jet combustion chambers having exhaust conduit-s at their rear ends, said chambers being positioned substantially normal to radii of said output shaft, whereby to effect rotation of the chambers by jet reaction, means gearingly coupling said housing member -to said output shaft, and means to admit liquid fuel into said one end portion of the housing member. f

6. A rotary jet engine comprising a support, an output shaft journaled on said support, a rotor secured on said output shaft and having a plurality of peripheral rows of outwardly projecting radial inclined compressor vanes, a generally cylindrical housing member rotatably mounted on said shaft and having air inlet means at one end portion for admitting air into said one end portion, inwardly projecting baille elements on said housing member extending between the peripheral rows of vanes, outwardly projecting rigid -conduits secured to and communieating with the other end portion of the housing member, respective jet combustion chambers mounted on the outer ends of said conduits, `said chambers hafving venturi air intake elements, fuel ignition means in said jet combustion chambers, said jet combustion chambers having exhaust conduits at their rear ends, said chambers being positioned substantially normal to radii of said output shaft, whereby to effect rotation of the chambers by jet reaction, means gearingly coupling said housing member to said output shaft, and means lto admit liquid fuel into said one end portion of the housing member.

l7. A rotary jet engine comprising a support, an output shaft journaled on said support, a rotor secured on `said output shaft and having a plurality of peripheral rows of outwardly projecting radial inclined compressor vanes, a generally cylindrical housing member rotatably mounted on said shaft and surrounding said rotor, said housing member having air inlet means at one end portion thereof for admitting air into said one end portion, inwardly projecting baffle elements on said housing member extending between said peripheral rows of vanes, outwardly projecting rigid conduits secured to and communicating with the other end portion of the housing member, respective jet combustion chambers mounted on the outer ends of said conduits, said chambers having venturi air intake elements communicating with said conduits and having air scoop portions at their forward ends communicating with said venturi elements, fuel ignition means in said jet combustion chambers, said jet combustion chambers having exhaust conduits at their rear ends, said chambers being positioned substantially normal to radii of said output shaft, whereby to effect rotation of the chambers by jet reaction, means gearingly coupling said housing member to said output shaftfand being constructed and arranged to rotate the output shaft in a direction opposite to the direction of rotation of the housing member, and means to admit liquid fuel into said one end portion of the housing member.

8. A rotary jet engine comprising a support, an output shaft journaled on said support, a rotor secured on said output shaft and having a plurality of peripheral rows of outwardly projecting radial inclined compressor vanes,

Y a generally cylindrical housing member rotatably mountother end portion of thehousing member, respective jet combustion chambers mounted on the outer ends of said conduits, said chambers having venturi air intake elements communicating with said conduits and having air scoop portions at their forward ends communicating with said venturi elements, fuel ignition means in said jet combustion chambers, said jet combustion chambers having exhaust conduits at their rear ends, said chambers being positioned substantially normal to radii of said output shaft, whereby to effect rotation of the chambers by jet reaction, a driven gear mounted on the output shaft, a ring gear mounted on the housing member concentrically with said driven gear, a plurality of planetary gears disposed between and gearingly coupling the ring gear to the driven gear, whereby to rotate the output shaft in a direction opposite to the direction of rotation of the housing member, and means to admit liquid fuel into said one end portion ofthe housing member.

References Cited in the file of this patent UNITED STATES -PATENTS 1,408,753 Long Mar. 7, 1922 1,934,237 Russell i- Nov. 7, 1933 2,680,949 IButler June 15, 1954 2,709,889 Mount June 7, 1955 FOREIGN PATENTS 366,450 Great Britain Mar. 3, 1932 440,500 Great Britain Jan. l, 1936 

1. A ROTARY JET ENGINE COMPRISING A MAIN HOUSING HAVING AIR INLET AND OUTLET PASSAGES, AN OUTPUT SHAFT JOURNALED IN SAID MAIN HOUSING, A ROTOR SECURED ON SAID OUTPUT SHAFT AND HAVING OUTWARDLY PROJECTING COMPRESSOR VANES, AN INNER HOUSING ROTATABLY MOUNTED ON SAID SHAFT AND HAVING AIR INLET MEANS OPENING INTO SAID MAIN HOUSING ADJACENT SAID AIR INLET PASSAGES, A SPACE BEING PROVIDED BETWEEN SAID INNER HOUSING AND SAID ROTOR, OUTWARDLY PROJECTING RIGID CONDUITS SECURED TO SAID INNER HOUSING AND COMMUNICATING WITH THE SPACE BETWEEN SAID INNER HOUSING AND SAID ROTOR, RESPECTIVE JET COMBUSTION CHAMBERS MOUNTED ON THE ENDS OF SAID CONDUITS, SAID CHAMBERS HAVING VENTURI AIR INTAKE ELEMENT COMMUNICATING WITH SAID CONDUITS AND HAVING AIR SCOOP PORTIONS AT THEIR FORWARD ENDS COMMUNICATING WITH SAID VENTURI ELEMENTS, FUEL IGNITION MEANS IN SAID JET COMBUSTION CHAMBERS, SAID JET COMBUSTION CHAMBERS HAVING EXHAUST CONDUITS AT THEIR REAR ENDS ADJACENT SAID OUTLET PASSAGES, SAID CHAMBERS BEING POSITIONED SUBSTANTIALLY NORMAL TO RADII OF SAID OUTPUT SHAFT, WHEREBY TO EFFECT ROTATION OF THE CHAMBERS BY JET REACTION, MEANS GEARINGLY COUPLING SAID INNER HOUSING TO SAID OUTPUT SHAFT, AND MEANS TO ADMIT LIQUID FUEL INTO THE SPACE BETWEEN THE INNER HOUSING AND SAID ROTOR. 